Aircraft humidifier

ABSTRACT

An aircraft humidifier is engineered as a stand-alone, fully integrated aircraft humidifier that is suitable for providing uniform, non-wetting humidified air disbursed by the aircraft humidifier into ambient air to increase the relative humidity in low humidity environments such as aircraft interiors, including cockpits, cabins, crew rests, cargo holds, and lavatories as well as any other enclosed areas.

CROSS-REFERENCE TO RELATED APPLICATION

This application is a continuation of U.S. patent application Ser. No.14/033,376, filed Sep. 20, 2013, which in turn claims the benefit ofU.S. Provisional Patent Application No. 61/703,690, filed Sep. 20, 2012,both of which are incorporated herein by reference.

TECHNICAL FIELD

The present subject matter generally relates to aircraft environmentalcontrol systems, and more particularly, it relates to humidity control.

BACKGROUND

The environmental control system of an aircraft provides air supply,thermal control, and cabin pressurization for the crew and passengers.The atmosphere at typical jetliner cruising altitudes is generally verydry and cold, and outside air is pumped into the cabin on a long flight.Consequently, when humid air at lower altitudes is encountered and drawnin, the environmental control system dries it through the warming andcooling cycle, so that even with high external relative humidity, insidethe cabin it will usually be not much higher than 10% relative humidity.Although low cabin humidity has health benefits such as preventing thegrowth of fungi and bacteria, the low humidity causes a drying of theskin, eyes, and mucosal membranes and contributes to dehydration, whichleads to fatigue, discomfort, and health issues.

SUMMARY

This summary is provided to introduce a selection of concepts in asimplified form that are further described below in the DetailedDescription. This summary is not intended to identify key features ofthe claimed subject matter, nor is it intended to be used as an aid indetermining the scope of the claimed subject matter.

One aspect of the present subject matter includes a device form whichrecites an aircraft humidifier comprising a water filtration system thatis suitable to produce filtered water without freezing, the waterfiltration system operating by static water pressure from an aircraftand including stages selected from a group consisting essentially ofreverse osmosis and deionization. The aircraft humidifier furthercomprises a duct that is capable of receiving atomized water dropletsformed from the filtered water and compressed air to communicate theatomized water droplets to ambient air. The duct includes a mouth,throat, neck, and a mix joint to receive the atomized water droplets,which together communicate the atomized water droplets to a chute,C-joint, and canal, which together in turn communicate the atomizedwater droplets to the ambient air through a posterior air outlet whileevaporating remaining atomized water droplets inside the duct.

Another aspect of the present subject matter includes a method formwhich recites a method for humidifying an aircraft cabin. The methodcomprises filtering water without freezing by operating static waterpressure from an aircraft and producing filtered water by causing thewater to enter stages of reverse osmosis, deionization, and finalfiltering. The method further comprises communicating atomized waterdroplets into ambient air through a duct that is capable of receivingatomized water droplets formed from the filtered water and compressedair while evaporating remaining atomized water droplets inside the duct.

DESCRIPTION OF THE DRAWINGS

The foregoing aspects and many of the attendant advantages of thisinvention will become more readily appreciated as the same become betterunderstood by reference to the following detailed description, whentaken in conjunction with the accompanying drawings, wherein:

FIG. 1 is a pictorial diagram illustrating an environment in which anarchetypical aircraft humidifier operates in accordance with oneembodiment of the present subject matter;

FIG. 2 is an isometric, perspective view illustrating an archetypicallidded aircraft humidifier in accordance with one embodiment of thepresent subject matter;

FIG. 3 is an isometric, perspective view of an archetypical unliddedaircraft humidifier assemblage in accordance with one embodiment of thepresent subject matter;

FIG. 4 is another isometric, perspective view of an archetypicalaircraft humidifier assemblage in accordance with one embodiment of thepresent subject matter;

FIG. 5 is a further isometric, perspective view of an archetypicalaircraft humidifier assemblage in accordance with one embodiment of thepresent subject matter;

FIG. 6 is a top plan view illustrating an archetypical aircrafthumidifier assemblage in accordance with one embodiment of the presentsubject matter;

FIG. 7 is an additional isometric, perspective view of an archetypicalaircraft humidifier assemblage in accordance with one embodiment of thepresent subject matter;

FIG. 8 is an isometric, front perspective view illustrating anarchetypical duct in accordance with one embodiment of the presentsubject matter;

FIG. 9 is an isometric, back perspective view illustrating anarchetypical duct in accordance with one embodiment of the presentsubject matter;

FIG. 10 is a top plan view illustrating an archetypical duct inaccordance with one embodiment of the present subject matter;

FIG. 11 is a front view of an archetypical duct in accordance with oneembodiment of the present subject matter;

FIG. 12 is a bottom plan view of an archetypical duct in accordance withone embodiment of the present subject matter;

FIG. 13 is a back view of an archetypical duct in accordance with oneembodiment of the present subject matter;

FIG. 14 is a pictorial diagram illustrating an archetypical method forcontrolling an aircraft humidifier in accordance with one embodiment ofthe present subject matter;

FIG. 15a is an isometric, perspective view of an archetypical assembledduct 1500 in accordance with another embodiment of the present subjectmatter;

FIG. 15b is an isometric, exploded, perspective view of an archetypicalunassembled duct 1500 in accordance with another embodiment of thepresent subject matter; and

FIG. 15c is a plan view of an archetypical duct 1500 in accordance withanother embodiment of the present subject matter.

DETAILED DESCRIPTION

Various embodiments of the present subject matter engineer an aircrafthumidifier. Some embodiments engineer a stand-alone, fully integratedaircraft humidifier that is suitable for providing uniform, non-wettinghumidified air disbursed by the aircraft humidifier into ambient air toincrease the relative humidity in low humidity environments such asaircraft interiors, including cockpits, cabins, crew rests, cargo holds,and lavatories, as well as any other enclosed areas. The term“non-wetting” means the inclusion of a condition in which water isevaporated in air that is above the dew point. In many embodiments, theaircraft humidifier is engineered to include a water source, a supply ofwater, a water filter, compressed air, a specialized nozzle withoutmoving parts, a duct (including, in some embodiments, a turbulator or anevaporator) to provide for maximum evaporation through the atomizationof water, and an internal drainage and collection system to collect andrecycle any loose un-evaporated water within the device to provide for asafe, sanitary and microbe-free environment. Depending on the interioraircraft dew point, in a few embodiments, it is engineered so that theproduced humidification is not wetting to surfaces external to theaircraft humidifier by evaporating the water and the air, and surfacetemperatures are caused to be above the dew point of the humid air orvice versa.

FIG. 1 illustrates an aircraft cabin 100, an environment in which anaircraft humidifier 103 operates. The aircraft humidifier is a devicethat is capable of improving breathing air quality by increasingrelative humidity for the crew and/or the passengers in the aircraftcabin 100 including a locally delimited area and a region surroundingthe locally delimited area. The aircraft cabin 100 is a section of anaircraft in which passengers lounge for traveling. At cruising altitudesof modern aircraft, the surrounding atmosphere is too thin forpassengers and crew to breathe without an oxygen mask, so cabins aretypically pressurized at a higher pressure than the ambient pressure atvarious altitudes.

In commercial air travel, particularly in airliners, cabins may bedivided into several parts. These can include travel class sections inmedium and large aircraft, areas for flight attendants, the galley, andstorage for in-flight services. Seats are primarily arranged in rows andalleys. Along these alleys, an aircraft galley service trolley 102 maybe pushed or pulled by flight attendants to facilitate in-flightservices to passengers. In various embodiments of the present subjectmatter, the aircraft humidifier 103 is housed by the aircraft galleyservice trolley 102 so as to facilitate humidifying the aircraft cabin100. In a few embodiments, the aircraft humidifier 103 is suitablyconnected to an aircraft environmental control system (not shown)instead of being housed by the aircraft galley service trolley 102.

FIG. 2 illustrates the aircraft humidifier 103 that is covered. In a fewembodiments, the aircraft humidifier 103 is engineered so as to have acapacity to provide healthier air for passengers and crew. The aircrafthumidifier 103 includes a lid 211 to protect the internal aircrafthumidifier assemblage. A control jack 209 is provided on a side of thelid 211 to allow a remote controller 205 to connect to the control jack209 so as to facilitate programming or controlling the aircrafthumidifier 103 via a control wire 207. In a few embodiments, the remotecontroller 205 interfaces with the aircraft humidifier 103 wirelessly,such as through Wi-Fi broadcasting in the aircraft cabin 100.

FIGS. 3-7 illustrate the aircraft humidifier assemblage with the lid 211removed. The aircraft humidifier assemblage includes a water filtersystem 322. The water filter system 322 is coupled to a water source(not shown) to produce filtered water. In one embodiment, the watersource is provided by a potable water supply on the aircraft; yet inanother embodiment, the water source is a reservoir within the aircrafthumidifier 103. In one embodiment, the water filter system 322 issuitably a three-stage system that includes a reverse osmosis stage, adeionized stage, and a final filtration stage. In two or threeembodiments, the three-stage system uses aircraft static water pressureto operate, but nothing else. In some embodiments, the holding tank issuitably not used. In a few embodiments, the water filter system 322 isengineered to facilitate antifreeze. A water feed line (not shown)communicates the filtered water to a valve 331. The valve 331 issuitable for regulating the communication of filtered water to a nozzle329.

The aircraft humidifier assemblage includes a pressurized air tank 313,which stores pressurized air. The aircraft humidifier assemblageincludes a compressor 323 which is coupled to the pressurized air tank313 to communicate pressurized air to be stored by the pressurized airtank 313. A pressurized air feed line (not shown) communicatespressurized air to the nozzle 329. In one embodiment, the compressor 323is not used and instead the pressurized air tank 313 receives bled airfrom the aircraft. In another embodiment, the compressor 323 is not usedand instead the pressurized air tank 313 receives compressed air fromthe aircraft. In a third embodiment, the compressor 323 is used toprovide compressed air directly to the pressurized air feed line feedingthe nozzle 329.

The nozzle 329 is engineered for projecting venting, without movingparts, the filtered water communicated by the water feed line and thepressurized air communicated by the pressurized air feed line, in oneembodiment, to produce atomized water droplets. In a second embodiment,the nozzle 329 is engineered to speed up, without moving parts, thefiltered water communicated by the water feed line and the pressurizedair communicated by the pressurized air feed line, to produce atomizedwater droplets. In a third embodiment, the nozzle 329 is engineered toaccelerate the filtered water communicated by the water feed line andthe pressurized air communicated by the pressurized air feed line, toproduce atomized water droplets.

The atomized water droplets (or exhausted humidified air) arecommunicated by the nozzle 329 to a duct 315 (duct, turbulator duct,evaporator duct, exhaust duct, and mixing duct may be usedinterchangeably). The duct 315, in one embodiment, is engineered toincorporate corrugated internal surfaces to agitate the evaporation ofatomized water droplets. In a second embodiment, the duct 315 isengineered to facilitate a spiral curvilinear passage. In a thirdembodiment, the spiral curvilinear passage is suitably an expandingspiral. In a fourth embodiment, the spiral curvilinear passage issuitably a constant area spiral. In a fifth embodiment, the duct 315 isengineered to have variable side walls to minimize or maximize the rateof outflow. In almost all embodiments, the duct 315 is engineered tocause a further mixing of the air/water mixture in the form of atomizedwater droplets to ensure full evaporation.

A sump 317 is capable of collecting moisture leaking from the duct 315.Any leaked moisture is detected and communicated by a sump moisturesensor 319. Actual moisture in the sump 317 is communicated on a sumpwater recycle line 321 back to the water filter system 322. An air inletport 327 b is provided by the aircraft humidifier assemblage to allowair to enter into the compressor 323. The duct 315 is coupled to an airoutlet port 325 as well as to an air inlet port 327 a. The air outletport 325 communicates the atomized water droplets to a locally delimitedarea of the aircraft cabin 100 and so as to feed humidified air into thelocally delimited area of the aircraft cabin 100 during normal operationof the aircraft. In one embodiment, the atomized water droplets arecommunicated by the aircraft humidifier 103 to ambient air without theuse of the air outlet port 325. In another embodiment, the atomizedwater droplets are communicated to the environmental control system ofthe aircraft, which in turn communicates the atomized water droplets toambient air.

FIG. 7 illustrates the electronics portions of the aircraft humidifierassemblage in greater detail. The aircraft humidifier assemblageincludes a DC-DC converter 723, an AC power isolator 725, a diode module727, a series of relays 729, sensors (not shown), and solenoids (notshown). The DC-DC converter 723 converts DC voltage of the aircraft to aDC voltage that powers the remote controller 205. The diode module 727is a rectifier portion of a DC circuit (a combination of the aircraft'sDC voltage source, the DC-DC converter 723, and the diode module 727),which acts to isolate the remote controller from the aircraftelectrically. The AC power isolator 725 acts to isolate the alternatingcurrent source of the aircraft from those portions of the aircrafthumidifier assemblage (e.g., the water filter system 322 and thecompressor 323).

FIGS. 8-13 illustrate the duct 315 in greater detail. The duct 315includes a mouth 831 that has the capacity to receive the atomized waterdroplets from the nozzle 329. The mouth forms a circular orifice that islarger than the diameter of a throat 833. The atomized water dropletsare communicated from the mouth 831 to the throat 833, and then theatomized water droplets traverse through a neck 835. The neck 835 isconical with its apex terminated at an angle. The neck 835 communicatesthe atomized water droplets to a mix joint 837. Coupled to the mix joint837 is a chute 839 through which the atomized water droplets are furthercommunicated. The chute 839 is suitable for communicating the atomizedwater droplets longitudinally along its length to a C-joint 841. TheC-joint 841 communicates the atomized water droplets to a canal 843.Coupled to the canal 843 is the sump 317 located at the bottom of thecanal 843. The canal 843 then communicates the atomized water dropletsalong its length, which is parallel to the chute 839 to a posteriorjoint 845 where the atomized water droplets exit through the posterioroutlet 847. Suitably, the posterior outlet 847 is an annular opening.The mix joint 837 is also coupled to an air cavity 851 which at itsterminal is an anterior air inlet 849. Suitably, the air cavity 851 islocated perpendicularly to the chute 839 when fastened to the mix joint837. Inside the air cavity 851, a fan 1153 is housed.

In one embodiment, the aircraft humidifier 103 is engineered to have ametallic or a composite liner which is water resistant and non-permeableto prevent leakage or contamination. In another embodiment, the aircrafthumidifier 103 is engineered to include internal mechanisms to evaporatefree water within the device. In a further embodiment, the aircrafthumidifier 103 is engineered to recycle any free water within the devicefor deployment as humidification. In an additional embodiment, theaircraft humidifier 103 is engineered to facilitate access to internalcomponents for maintenance, repair, and cleaning. In a concreteembodiment, the aircraft humidifier 103 is engineered to incorporateanalog and/or digital controls for monitoring, switching, transmitting,metering, measuring, sensing, lighting, cleaning, and connecting toexisting environmental control systems. In a specific embodiment, theaircraft humidifier 103 is engineered to be incorporated in a customizedcontainer which is the size of a typical aircraft galley service trolleyand which then may be incorporated into the galley trolley insertlocations with typical locking and docking mechanisms. In a latestembodiment, the aircraft humidifier 103 is engineered to include wheelsor other mechanisms for mobility. In a latter embodiment, the aircrafthumidifier 103 is engineered to be incorporated into the overheadstorage bin of the aircraft's passenger cabin. In a latter embodiment,the aircraft humidifier 103 is engineered to be incorporated above orbelow the aircraft's passenger cabin. In an as yet further embodiment,the aircraft humidifier 103 is engineered to disperse disinfectants orother water soluble compounds into ambient air.

FIG. 14 illustrates an archetypical method 1500 for controlling anaircraft humidifier. A controller 1520 communicates with a relay 1510 toopen or close a valve 1506 so as to allow water from an aircraft 1502which has been filtered by a filter 1504 (which is capable of reverseosmosis, deionization, and so on) to the valve 1506 so as to enter anozzle 1532. A voltage source 1516, which in one embodiment isalternating current rated at 115 volt, 400 hertz, 3-phase from theaircraft, is coupled to an AC power isolator 1518. The power coming outfrom the AC power isolator 1518 is communicated to a relay 1508 tocontrol the filter 1504 and a relay 1528 to control an air compressor1540. A direct current power source 1526 of approximately 18-32 volts iscommunicated to a diode module 1536. The diode module 1536 acts torectify the power coming from the DC voltage source 1526 andcommunicates the power to a DC-DC converter 1530. The converted power ispresented to the controller 1520 to power it. Air source 1538 isprovided by the aircraft and is provided to both the air compressor 1540as well as to a fan 1544. The air compressor 1540 compresses the airfrom the air source 1538 and presents the compressed air to the nozzle1532. The resultant air product (in the form of atomized water droplets)coming from the nozzle 1532 is presented to a turbulator or exhaust duct1534. The fan 1544 also conducts air through a duct 1542 and also to theturbulator or exhaust duct 1534. The air moves through a moisture sensor1524, which communicates its findings back to the controller 1520 andpermits the air to enter the cabin and flight deck air 1514. The method1500 supplies humidified air into the aircraft cabin 100, including alocally delimited area and a region surrounding the locally delimitedarea. The method 1500 humidifies the air with a water source. The method1500 then feeds the humidified air at the first partial pressure througha feed line into the locally delimited area during normal operation ofthe aircraft. The first partial pressure is higher than a second oxygenpartial pressure in the region surrounding the locally delimited area.

While illustrative embodiments have been illustrated and described, itwill be appreciated that various changes can be made therein withoutdeparting from the spirit and scope of the invention.

The embodiments of the invention in which an exclusive property orprivilege is claimed are defined as follows:
 1. An aircraft humidifiercomprising: a water filtration system that is suitable to producefiltered water without freezing, the water filtration system operatingby static water pressure from an aircraft and including stages selectedfrom a group consisting essentially of reverse osmosis and deionization;a filtering relay coupled to the water filtration system; and a ductthat is capable of receiving atomized water droplets formed from thefiltered water and compressed air to communicate the atomized waterdroplets to ambient air, the duct including a mouth, throat, neck, and amix joint to receive the atomized water droplets, which togethercommunicate the atomized water droplets to a chute, C-joint, and canal,which together in turn communicate the atomized water droplets to theambient air through a posterior air outlet while evaporating remainingatomized water droplets inside the duct.
 2. The aircraft humidifier ofclaim 1, wherein the duct further includes an air cavity and an anteriorair inlet, which communicates air through the air cavity into the mixjoint, the air cavity including a fan.
 3. The aircraft humidifier ofclaim 2, further comprising a compressor which compresses air to producethe compressed air.
 4. The aircraft humidifier of claim 2, furthercomprising a compressing relay which is coupled to the compressor whichcompresses air to produce the compressed air.
 5. The aircraft humidifierof claim 4, further comprising a pressurized air tank for storing thecompressed air produced by the compressor.
 6. The aircraft humidifier ofclaim 5, further comprising a valve which has a capacity to receive thefiltered water and communicate the filtered water.
 7. The aircrafthumidifier of claim 6, further comprising a valve relay which is coupledto the valve.
 8. The aircraft humidifier of claim 7, further comprisinga nozzle which is suitable for receiving the filtered water from thevalve and the compressed air from the compressor, the nozzlecommunicating the atomized water droplets to the duct.
 9. The aircrafthumidifier of claim 8, further comprising a sump coupled to the duct,which is capable of collecting moisture leaking from the duct.
 10. Theaircraft humidifier of claim 9, further comprising a sump moisturesensor coupled to the sump, which has a capacity to detect moisture andcommunicate such a detection.
 11. The aircraft humidifier of claim 10,further comprising a water recycle line coupled to the sump, which issuitable for communicating moisture from the sump back to the waterfilter system.
 12. An aircraft humidifier comprising: a water filtrationsystem that is suitable to produce filtered water without freezing, thewater filtration system operating by static water pressure from anaircraft and including stages selected from a group consistingessentially of reverse osmosis and deionization; and a duct that iscapable of receiving atomized water droplets formed from the filteredwater and compressed air to communicate the atomized water droplets toambient air, the duct including a spiral curvilinear passage in itsinternal surfaces, a portion of which is corrugated to agitate theevaporation of atomized water droplets, the spiral curvilinear passagewinding around a center and gradually receding from or approaching thecenter.
 13. The aircraft humidifier of claim 12, wherein the ductfurther includes an air cavity which includes a fan.
 14. The aircrafthumidifier of claim 13, further comprising a compressor which compressesair to produce the compressed air.
 15. The aircraft humidifier of claim14, further comprising a compressing relay which is coupled to thecompressor which compresses air to produce the compressed air.
 16. Theaircraft humidifier of claim 15, further comprising a pressurized airtank for storing the compressed air produced by the compressor.
 17. Theaircraft humidifier of claim 16, further comprising a valve which has acapacity to receive the filtered water and communicate the filteredwater.
 18. The aircraft humidifier of claim 17, further comprising avalve relay which is coupled to the valve.
 19. The aircraft humidifierof claim 18, further comprising a nozzle which is suitable for receivingthe filtered water from the valve and the compressed air from thecompressor, the nozzle communicating the atomized water droplets to theduct.
 20. The aircraft humidifier of claim 19, further comprising an ACpower isolator coupled to the filtering relay and the compressing relay.